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July 18, 2012, 17:12 |
Theory of Aerodynamic Coefficients
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#1 |
New Member
Mark
Join Date: Mar 2012
Posts: 20
Rep Power: 14 |
Hello,
I have simulated some the flow field around a NACA profile. I would like to compare Cl, Cd,Cn, Cm gotten with CFD with theoretical expression. I know a very interesting book "Theory of Wing Sections" to compare my results but I am wondering if there is a free software which you choose the profile, flow conditions (Mach, Reynolds and angle) and it calculates the aerodynamic coefficients. Thanks in advance! |
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July 18, 2012, 22:34 |
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#2 |
Senior Member
KHB
Join Date: Aug 2010
Location: Singapore
Posts: 118
Rep Power: 15 |
Have you tried xfoil?
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July 18, 2012, 23:01 |
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#3 |
Senior Member
ATM
Join Date: May 2009
Location: United States
Posts: 104
Rep Power: 16 |
Check out the NASA website for "Foilsim". They are updating it to a new version, but I believe the applet gives reasonable estimates for the airfoils based on experimental data.
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July 27, 2012, 04:35 |
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#4 |
New Member
Mark
Join Date: Mar 2012
Posts: 20
Rep Power: 14 |
Thanks!! I could calculate with Xfoil tool
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